Thermally compliant fitting for high temperature tube applications

Abstract

A fitting is configured to couple a portion of a frame of a turbine and a bearing housing on an aircraft engine. The fitting includes a first receptacle configured to seat a tube that is configured to convey oil or air, and at least a second receptacle configured to seat a corresponding at least two bolts associated with the bearing housing, wherein the fitting comprises sections between the first receptacle and the at least a second receptacle that have a material thickness in a range of 3.175 millimeters and 6.35 millimeters.

What is claimed is: 
     
       1. A system assembly, comprising:
 at least one tube; 
 a bearing housing of an engine; and 
 a fitting that includes:
 a first receptacle configured to seat the at least one tube; and 
 at least a second receptacle configured to seat and encapsulate a corresponding at least one bolt associated with the bearing housing, 
 wherein the fitting comprises sections between the first receptacle and the at least a second receptacle that have a material thickness in a range of 3.175 millimeters and 6.35 millimeters. 
 
 
     
     
       2. The system assembly of  claim 1 , wherein the sections are approximately 5.1 millimeters thick. 
     
     
       3. The system assembly of  claim 1 , wherein the at least a second receptacle comprises three receptacles configured to seat three corresponding bolts. 
     
     
       4. The system assembly of  claim 1 , further comprising:
 a seal groove that is substantially located around the perimeter of the fitting. 
 
     
     
       5. The system assembly of  claim 4 , wherein the at least a second receptacle is located inward of the seal groove relative to the perimeter of the fitting. 
     
     
       6. The system assembly of  claim 1 , wherein the at least one tube is configured to convey oil or air. 
     
     
       7. The system assembly of  claim 1 , wherein the at least one tube conveys oil.